JP2587577B2 - Gas turbine device and fuel nozzle assembly thereof - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION The present invention relates to fuel nozzles for gas turbines, and more particularly, to fuel nozzle assemblies having replaceable nozzle caps.

[0002] Gas turbines include a combustion system having one or more combustors adapted to generate hot gas by burning fuel in compressed air. A fuel nozzle assembly is used to introduce fuel into each combustor.

[0003] Traditionally, fuel nozzles consist of a nozzle base and a nozzle cap. The nozzle base has an inlet port for receiving fuel to be burned, and the fuel nozzle assembly is attached to the combustion system by bolting the inlet port to the combustor itself or to a cylinder surrounding the combustor. . The nozzle cap is provided with fuel outlet ports, which serve to inject fuel into the combustor. Generally, the nozzle cap extends from the nozzle base into the interior of the combustor. The nozzle cap is subject to degradation due to combustion, erosion and corrosion due to its proximity to the flame front and hot combustion gases within the combustor. As a result, the nozzle cap must be replaced relatively frequently.

Gas turbines operate on a variety of fuels, including liquid and gaseous fuels, and may require steam injection into the combustor to minimize the formation of environmental pollutants, NOx. Current fuel nozzle assemblies must be able to introduce at least two types of fluids into the combustor. Thus, to facilitate quick switching from one fuel to another, the fuel nozzle assembly employs a so-called "dual fuel" so that the need to change nozzles when changing fuel is avoided. Often manufactured in a model. In addition, some fuel nozzle assemblies are of the gas / steam type, manufactured for emission control purposes.

[0005] In order to meet the requirements imposed on fuel nozzle assemblies that they must be able to introduce two different fluids into the combustor, current fuel nozzle assemblies include relatively complex internals. It has a passage structure. Generally, the nozzle cap is connected to the nozzle base via inner and outer sleeves, where the inner and outer sleeves transfer gas fuel from an inlet port formed in the nozzle base to an outlet formed in the nozzle cap. It defines an annular passage towards the port. Further, in the case of a gas / oil switching dual fuel nozzle assembly, a central cavity or chamber is formed to accommodate the oil injection nozzle, and in the case of a "gas / steam" nozzle assembly, the nozzle base. A passage is formed that directs steam from an inlet port formed in the nozzle cap to an outlet port formed in the nozzle cap.
As a result of such complex geometries of conventional fuel nozzle assemblies, the nozzle base and nozzle cap have been manufactured as one-piece cast parts or as welded structures.

As a result of such an integral structure, when replacing the nozzle cap, it is necessary to remove the old nozzle cap from the nozzle base by grinding and weld a new nozzle cap. This operation requires special tools and skilled workers. Therefore, it was necessary to transfer the fuel nozzle from its installation location to an external repair facility. Thus, the need to remove the fuel nozzles from the power plant significantly increases the cost and downtime of maintenance of the combustion system, and is one of the maintenance issues for the user.

Accordingly, it is possible to burn two or more fuels or to burn gas fuel while injecting steam, and to easily separate the nozzle cap from the nozzle body. It is desirable to have a fuel nozzle assembly for a gas turbine that allows the user to easily replace the nozzle cap.

[0008]

SUMMARY OF THE INVENTION Accordingly, it is a general object of the present invention to provide a method for burning two or more fuels or burning gaseous fuel while injecting steam, and for replacing a nozzle cap. The present invention provides a fuel nozzle assembly for a gas turbine that enables the user to easily separate the fuel nozzle from the nozzle body so that the user can easily execute the nozzle.

Briefly, the above and other objects of the present invention are: (i) a compressor for generating compressed air;
i) a combustion system for heating compressed air with fuel to produce heated compressed gas; (iii) a fuel nozzle assembly for introducing fuel into the combustion system; A turbine for expanding heated compressed gas, the fuel nozzle assembly comprising:
(I) a nozzle base having fixing means for fixing the fuel nozzle assembly to a combustion system; and (ii) a first fluid outlet port configured to inject fluid into the compressed air. A nozzle cap having rearwardly extending inner and outer sleeves; and (iii) coupling / separation means for coupling the nozzle base to the nozzle cap and separating the nozzle base from the nozzle cap. The means is achieved by a fuel nozzle assembly having first and second mounting and dismounting means for attaching and detaching the nozzle base to the inner and outer sleeves, respectively, from the inner and outer sleeves.

In a preferred embodiment of the present invention, the inner sleeve has means for accommodating a difference in thermal expansion between the inner sleeve and the outer sleeve, and includes first and second mounting and removing means. The outer means comprises first and second screw members, respectively. The first screw member constitutes means for pulling the inner sleeve against the nozzle base, and the second screw member
Of the threaded member constitute means for pressing the outer sleeve against the nozzle base. Further, the coupling / separation means includes means for preventing the nozzle cap from rotating with respect to the nozzle base, and first and second seals respectively disposed between the nozzle cap and the inner and outer sleeves. I do.

[0011]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Referring to the drawings, FIG.
The gas turbine device 100 is shown in a schematic diagram. The gas turbine device 100 includes a turbine 1 via a shaft 105.
The compressor 102 is driven by the compressor 04.
The surrounding air 107 is sucked into the compressor 102 and compressed. Compressed air 10 generated by compressor 102
8 is directed to the combustion system. The combustion system comprises one or more combustors 103, a fuel nozzle assembly 1 for each combustor, and a cylinder 53 (shown in broken lines in FIG. 2) surrounding the combustor. . In the combustor 103, the fuel 109 is burned in the compressed air 108, thereby generating a hot compressed gas 112. In that case, the fuel 109
Is No. It can be a liquid such as distillate or a gas such as natural gas, and is introduced into the combustor 103 by the fuel nozzle assembly 1.

The compressed gas 1 generated by the combustor 103
12 is sent to a turbine 104 where it is expanded, thereby producing a rotational output for driving a load such as a compressor 102 and a generator 106. Turbine 104
The expanded compressed gas 112 generated by the above is discharged directly to the atmosphere or, in a combined cycle power plant, is first sent to a heat recovery steam generator and then discharged to the atmosphere.

FIG. 2 shows a "gas / oil" fuel nozzle assembly 1 with a removable "gas / oil" nozzle cap 4 according to the present invention. In addition to nozzle cap 4,
The nozzle assembly 1 includes a nozzle base 3 and an oil injection nozzle 34.
And a swirl plate 6 and a ring 5. A flange 36 is formed in the nozzle base 3, and the nozzle base is fixed to a cylindrical body 53 surrounding the combustor 103 by using a screw (not shown). Further, the nozzle base 3 is provided with a gas fuel inlet port (first fluid inlet port) 14 and a port 38 (second fluid inlet port), which are of a conventional type. And extends into the central chamber 8.

In operation, gas fuel 110 flows into a gas fuel inlet port 14 provided in the nozzle base 3 and from there into a manifold 15 through which a number of passages 39 are provided. Distributed to From the passage 39, the gas passes through the annular passage 16 and a plurality of gas fuel outlet ports (first fluid outlet ports) 18 arranged around the surface of the nozzle cap 4.
Flows to The gas fuel outlet port 18 is connected to the combustor 103.
And serves to inject gas fuel 110 into the compressed air 108. The oil fuel 109 flows into the oil injection nozzle 34 via the inlet port 37. The oil injection nozzle 34 is connected to an oil fuel outlet port (second port) formed on the surface of the nozzle cap 4.
The oil fuel is injected into the compressed air through the fluid outlet port 19 of the first embodiment.

The oil fuel nozzle is coked at the outlet port 19. Therefore, in addition to the oil fuel 109 and the gas fuel 110, the cooling air 115 taken in from the compressed air 108 discharged from the compressor is also supplied to the fuel nozzle assembly 1. In connection therewith, a cooling air passage 17 extending in the radial direction is arranged around the nozzle base 3.
The inlets of these cooling air passages are in fluid communication with the compressed air flowing into combustor 103. From the cooling air passage 17, the cooling air is directed to the central chamber 8 in which the oil injection nozzle 34 is disposed, through an opening 42 provided in the lock pipe (first screw member) 10 described in detail later. . The cooling air 115 is supplied to the inner sleeve 11 and the oil injection nozzle 34.
Flows along the annular space between the oil fuel outlet port 1
It flows out of the nozzle via 9. The cooling air serves to prevent the coking described above by cleaning the tip of the oil injection nozzle 34 and flowing through the oil fuel outlet port 19.

FIG. 3 shows a gas fuel nozzle assembly 2 having a steam injection capability and having a removable "gas / steam" nozzle cap 4 'according to the present invention. This "gas / steam" nozzle assembly 2 comprises an oil injection nozzle 34,
With the exception of the absence of the cooling air passage 17 and the oil outlet port 19, and the additional provision of a steam outlet port (second fluid outlet port) 27 around the face of the nozzle cap 4 ', FIG. 1 is essentially the same as the "gas / oil" nozzle assembly 1 shown in FIG.

In operation, gas fuel 110 flows into gas inlet port 14 formed in nozzle base 3 'and, as described above, gas fuel outlet via manifold 15, passage 39 and annular passage 16. Flows to port 18. The steam 114 enters the nozzle base 3 via the inlet port 38 and from there through the central chamber 8 to the steam outlet port 2.
Flows to 7. Steam outlet port 27 injects steam 114 into the hot gas within combustor 103, thereby reducing NOx formation.

As shown in FIG. 3, an annular gas fuel passage 16 is formed between the inner sleeve 11 and the outer sleeve 12 which are arranged concentrically. The outer sleeve 12 includes a front portion (second portion) 12 ′ extending rearward from the nozzle cap 4 ′ and a rear portion (first portion) 12 ″ extending forward from the nozzle base 3 ′. The rear part 12 "of the outer sleeve has a swirl plate 6
And flange 4 for attaching ring 5 with screw 41
0 is formed.

Similarly, the inner sleeve 11 has a front portion (second portion) 11 'extending rearward from the nozzle cap 4'.
And a rear portion (first portion) 11 ″ extending forward from the nozzle base 3 ′. An expansion joint 13 made of a metal expansion and contraction bellows is formed on the front portion 11 ′ of the inner sleeve 11. The elastic bellows 13 reduces the stress generated in the inner sleeve 11 due to the difference in thermal expansion between the inner sleeve 11 and the outer sleeve 12. Further, as shown in FIG. It is formed in the sleeve 11.

As already mentioned, it would be highly advantageous if the nozzle cap could be easily replaced without having to cut the inner and outer sleeves 11 and 12 connecting the nozzle cap to the nozzle base. However, due to the relatively complex configuration of the fuel nozzle assembly shown in FIGS. 2 and 3 and the flexibility afforded by the expansion joint 13 and limited access to the interior of the nozzle, a single unit for securing the nozzle cap to the nozzle base. Use of threaded joints is prohibited.

As will be described in detail later, according to the present invention,
This problem is solved by separating the nozzle cap from the nozzle base along two separate fittings, one in the inner sleeve and the other in the outer sleeve. In this case, each joint is fixed by a threaded locking member. The problem of limiting access to the interior of the nozzle is addressed by using an outer lock nut (first or outer lock member) 9 and an inner lock tube (second or inner lock member) 10. You. Outer lock nut 9
Is installed from the front of the nozzle assembly to crimp the mating portions of the outer sleeve joint together. An inner lock tube 10 is mounted from the rear of the fuel nozzle assembly to pull the mating portions of the inner sleeve joint together.
Although the following description of the present invention is made in connection with the "gas / steam" nozzle assembly 2 shown in FIG. 3, this description is also applied to the gas / oil nozzle assembly 1 shown in FIG. It should be understood that it is equally applicable.

Thus, as shown in FIG. 3, according to the present invention, the nozzle cap 4 'can be easily replaced by a connecting means for removably connecting the front and rear portions of the inner sleeve 11 and the outer sleeve 12 together. Has been. In particular, as best shown in FIG. 4, the front part 12 'and the rear part 12 "of the outer sleeve 12 are joined by a lock nut 9. The lock nut 9 is formed in the front part 12' of the outer sleeve. It has a male thread which is threaded with a female thread to form a threaded joint (first mounting and dismounting means) 24. The lock nut 9 has a flange 43 formed on the back of the front part 12 'of the outer sleeve. Pressing against the front surface 44, which is ground on the rear portion 12 "of the outer sleeve, forms a first rigid but detachable joint between the nozzle cap 4 'and the nozzle base 3'.

As shown in FIG. 3, the joint of the outer sleeve 12 is also provided with a seal 23 which can be a compressible hot gasket located in a groove formed in the surface 44. . The seal 23 prevents the gas fuel 110 flowing in the annular passage 16 from leaking into the compressed air surrounding the fuel nozzle assembly 2.

In addition, the joint of the outer sleeve 12 passes through aligned holes 28 and 29 formed in the face 44 of the rear portion 12 "of the outer sleeve and the flange 43 of the front portion 12 'of the outer sleeve, respectively. A locking anti-rotation pin 20 is provided, by means of which the friction between the locking nut 9 and the flange 43 causes the front portion 12 'of the outer sleeve during tightening of the locking nut.
Is reliably prevented from rotating. If such rotation occurs, a torque that may damage the expansion joint 13 may be applied to the inner sleeve. In addition, the anti-rotation pin 20 ensures that the angular configuration of the gas outlet port 18 and the steam outlet port 27 about the longitudinal axis of the nozzle is uniform for each fuel nozzle assembly, thereby providing combustion around the combustion system. Gas homogeneity is maximized.

As a result of using the expansion joint 13, the lock nut 9 for the outer sleeve 12 is
5 cannot transmit the force pressing the front part 11 'and the rear part 11 "together. Therefore, as best shown in FIG. The locking tube 10 described above is used to form the locking tube 10. The locking tube 10 has at its rear end a flange 45 which mates with a shoulder 46 formed in the port 38 of the nozzle base 3 '. In addition, the lock tube 10
Has at its front end a male thread that engages with a female thread formed at the rear end of the front portion 11 'of the inner sleeve. In this way, by engaging the front part 11 ′ of the inner sleeve, the locking tube 10 is brought into contact with the rear part 11 ″.
Pulls the front portion 11 'of the inner sleeve against, thereby forming a second rigid but separable joint between the nozzle cap 4' and the nozzle base 3 '.

As in the joint of the outer sleeve 12,
The joint of the inner sleeve 11 is provided with a seal 22, which can be a compressible hot gasket arranged in a groove formed in the front of the rear part 11 "of the inner sleeve. Is an annular gas passage 1
Communication between the central chamber 8 and the central chamber 8 is prevented, so that in the case of the "gas / steam" nozzle assembly 2 no gaseous fuel 110 flows into the steam flow 114 and the "gas / oil" nozzles In the case of the assembly 1, it is ensured that the gaseous fuel does not leak into the cooling air 115. Further, the inner sleeve 11
Each have a rear portion 11 "of the inner sleeve.
A rotation preventing pin 21 is provided which extends through aligned holes 30 and 31 provided on the front face of the inner sleeve and on the rear face of the front portion 11 'of the inner sleeve. This rotation prevention pin 21
This ensures that the front part 11 ′ of the inner sleeve is secured against rotation, so that the locking tube 10 can be tightened.

If, after a certain period of operation, the nozzle cap 4 'needs to be replaced, the nozzle assembly 2 is removed from the combustion system, the swirl plate 6 and the ring 5 are removed, and then the lock nut 9 and the lock pipe are removed. The old nozzle cap 4 'can be separated from the nozzle base 3' by removing 10 and a new nozzle cap can be attached to the nozzle base 3 '.

While the invention has been described with reference to oil / gas and gas / steam fuel nozzles, the invention is directed to other types of nozzles, particularly two or more fluids, for injection into a combustion system. It is equally applicable to existing fuel nozzles. Accordingly, the present invention may be embodied in other specific forms without departing from the spirit of the invention and its essential attributes,
The present invention is not limited to the embodiments described above.

[Brief description of the drawings]

FIG. 1 is a simplified schematic diagram of a gas turbine.

FIG. 2 is a cross-sectional view of a "gas / oil" fuel nozzle assembly having a replaceable nozzle cap according to the present invention.

FIG. 3 is a cross-sectional view of a gas fuel nozzle assembly having a replaceable nozzle cap and having steam injection capability according to the present invention.

FIG. 4 is a detailed view of the part indicated by the circle IV in FIG. 3 with the screw and the hole through which the screw is removed for clarity of illustration.

FIG. 5 is a detailed view of a portion indicated by a circle V in FIG.

[Explanation of symbols]

1, 2, ... fuel nozzle assembly, 3, 3 '... nozzle base,
4, 4 'nozzle cap, 9 lock nut (first screw member or outer lock member), 10 lock tube (second screw member or inner lock member), 11 inner sleeve, 11' inner sleeve The second part (front part), 11 "... the first part (rear part) of the inner sleeve, 12 ... the outer sleeve, 12 '... the second part (front part) of the outer sleeve, 12" ... the outer sleeve A first part (rear part) of the first fluid inlet port, 18
... first fluid outlet port, 19 ... second fluid outlet port, 27 ... second fluid outlet port, 24 ... threaded joint (first mounting and removing means), 25 ... threaded joint (second mounting)・
Removing means), 38 second fluid inlet port, 100 gas turbine device, 102 compressor, 103 combustion system (combustor), 104 gas turbine, 108 compressed air, 1
09: fuel, 110: fuel, 112: compressed gas.

Continuation of the front page (56) References JP-A-2-213605 (JP, A) JP-A-61-181916 (JP, U)

Claims (3)

(57) [Claims] 1. A gas turbine device, comprising: a) a compressor for generating compressed air; and b) a combustion system for heating the compressed air with an internal fuel to generate a heated compressed gas. C) a fuel nozzle assembly for introducing fuel into the combustion system, comprising: (i) a nozzle base having fixing means for fixing the fuel nozzle assembly to the combustion system; An integral nozzle cap having a first fluid outlet port configured to inject fluid into the compressed air and having rearwardly extending inner and outer sleeves; (iii) a separate nozzle cap from the nozzle cap and the nozzle base.
That has been released, the nozzle base to the nozzle cap
Means for releasably connecting said nozzle base to said nozzle base
Attach to the inner and outer sleeves
First and second for removal from the outer and outer sleeves respectively
The first mounting / removing means has two mounting / removing means .
Means for engaging said inner sleeve with said nozzle base.
A, the second attachment-detachment means before and said outer sleeve
Said coupling hand having means for engaging said nozzle base.
A fuel nozzle assembly comprising: a stage; and d) a turbine for expanding the heated compressed gas from the combustion system. 2. A gas turbine device having a combustion system for heating a compressed gas by burning fuel therein, comprising: a fuel nozzle assembly for introducing the fuel into the combustion system; A nozzle base having securing means for securing the fuel nozzle assembly to the combustion system and having first and second fluid inlet ports formed therein; and b) the first and second fluid outlet ports are provided. A nozzle cap formed; c) an inner and outer sleeve connecting the nozzle cap to the nozzle base, the inner and outer sleeves having first and second portions, respectively, wherein the first one of the inner and outer sleeves; Portions extending from the nozzle base and the second portions of the inner and outer sleeves extending from the nozzle cap; and d) in front of the outer sleeve. A first having coupling and separating means for coupling a first portion to the second portion of the outer sleeve and for separating the first portion of the outer sleeve from the second portion of the outer sleeve; E) coupling the first portion of the inner sleeve to the second portion of the inner sleeve or displacing the first portion of the inner sleeve from the second portion of the inner sleeve. A second generally annular threaded member having coupling and disconnection means for disconnection. 3. A gas turbine device having a combustion system for heating a compressed gas by burning fuel therein, comprising: a fuel nozzle assembly for introducing the fuel into the combustion system; A nozzle base having a fluid inlet port for receiving fuel for the fuel nozzle assembly; b) a nozzle cap having a fluid outlet port formed therein and having rearwardly extending inner and outer sleeves; An outer locking member for coupling to the nozzle base and separating the outer sleeve from the nozzle base, the outer lock having a threaded portion adapted to press the outer sleeve against the nozzle base; D) for coupling the inner sleeve to the nozzle base and separating the inner sleeve from the nozzle base; A side locking member, a fuel nozzle assembly and a said inner locking member having a threaded portion adapted to pull the same inner sleeve relative to the nozzle base.